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公开(公告)号：US10370971B2
公开(公告)日：2019-08-06
申请号：US14929771
申请日：2015-11-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco , Damon K. Brown , Nicholas Aiello
Abstract: A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.
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公开(公告)号：US20150369045A1
公开(公告)日：2015-12-24
申请号：US14740316
申请日：2015-06-16
Applicant: United Technologies Corporation
Inventor： Nicholas Aiello , Bob S. Bamford
CPC classification number: F01D5/02 , F01D5/027 , F01D5/141 , F01D5/16 , F02C3/04 , F05D2220/32 , F05D2230/60 , F05D2240/80 , F05D2260/941 , Y02T50/671 , Y02T50/673 , Y10T29/49323
Abstract: A rotor for a turbomachine includes a rim defining a base of a rotor, an airfoil shaped blade extending from said rim and defining a chord line and a bore extending from said rim opposite said airfoil shaped blade. The rim further includes at least one rail extending away from said airfoil shaped blade.
Abstract translation: 用于涡轮机的转子包括限定转子的基座的边缘，从所述边缘延伸并限定弦线和从所述翼缘相对于所述翼型叶片延伸的孔的翼型叶片。 轮辋还包括至少一个远离所述翼型刀片延伸的轨道。
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公开(公告)号：US10982555B2
公开(公告)日：2021-04-20
申请号：US14787013
申请日：2014-02-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas Aiello , John C. Duong
Abstract: A root extending from a platform of an airfoil is disclosed. The root may include a first portion having a generally cylindrical shape, and a second portion extending from the first portion to the platform. The second portion may have a circumference larger than a circumference of the first portion.
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公开(公告)号：US10458265B2
公开(公告)日：2019-10-29
申请号：US14783925
申请日：2014-03-19
Applicant: United Technologies Corporation
Inventor： Nicholas Aiello
Abstract: An integrally bladed rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a radially inner hoop extending circumferentially about an axis, a plurality of circumferentially spaced, axially extending slots, separated by respective blade supports, and a seal system that includes seal fingers extending axially through the slots.
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公开(公告)号：US10167729B2
公开(公告)日：2019-01-01
申请号：US14769951
申请日：2014-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas Aiello , Uyen Phan
Abstract: A knife edge seal includes a pedestal and a knife edge with a tip and a base. The base rests on the pedestal. The base has a first width and the tip has a second width, and the ratio of the first width to the second width is in the range of 5:1 to 15:1. A gas turbine engine and a method of sealing a high pressure area from a low pressure area are also disclosed.
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Patent Agency Ranking
公开(公告)号：US20180363480A1
公开(公告)日：2018-12-20
申请号：US16100615
申请日：2018-08-10
Applicant: United Technologies Corporation
Inventor： Nicholas Aiello , James Cosby
CPC classification number: F01D5/32 , F01D5/3038 , Y10T29/49321
Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.
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公开(公告)号：US09828865B2
公开(公告)日：2017-11-28
申请号：US13627036
申请日：2012-09-26
Applicant: United Technologies Corporation
Inventor： Nicholas Aiello , Raji Mali
IPC: F01D5/30
CPC classification number: F01D5/3038 , Y10T29/49332
Abstract: An example turbomachine rotor provides a groove that is annular and is configured to receive a root of an airfoil, the groove having a radial cross-sectional area. A ratio of the radial cross-sectional area of the groove to a radial cross-sectional area of the root received within the annular groove is from 2 to 5.
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公开(公告)号：US09803481B2
公开(公告)日：2017-10-31
申请号：US14740316
申请日：2015-06-16
Applicant: United Technologies Corporation
Inventor： Nicholas Aiello , Bob S. Bamford
CPC classification number: F01D5/02 , F01D5/027 , F01D5/141 , F01D5/16 , F02C3/04 , F05D2220/32 , F05D2230/60 , F05D2240/80 , F05D2260/941 , Y02T50/671 , Y02T50/673 , Y10T29/49323
Abstract: A rotor for a turbomachine includes a rim defining a base of a rotor, an airfoil shaped blade extending from said rim and defining a chord line and a bore extending from said rim opposite said airfoil shaped blade. The rim further includes at least one rail extending away from said airfoil shaped blade.
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公开(公告)号：US20160153463A1
公开(公告)日：2016-06-02
申请号：US14929701
申请日：2015-11-02
Applicant: United Technologies Corporation
Inventor： Anthony R. Bifulco , Damon K. Brown , Nicholas Aiello
CPC classification number: F04D29/321 , F01D5/02 , F01D5/066 , F01D11/001 , F01D25/28 , F02C3/06 , F05D2220/32 , F05D2240/24 , F05D2300/603 , F05D2300/6032 , F05D2300/614 , Y02T50/672
Abstract: A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material. As a gas turbine engine operates, the rotation creates forces which can deform, expand, contract or translate certain gas turbine engine components, including spacers. These forces can adversely affect gas turbine engine performance and reliability, particularly when they are either unpredictable or difficult to control. Reinforcing a spacer with a fiber may allow a lower system weight, more compact or configurable internal packaging or a high degree of reinforcement.
Abstract translation: 燃气涡轮发动机的间隔件用纤维增强。 纤维可以用基材固化以形成纤维增强复合材料。 当燃气涡轮发动机运行时，旋转产生能够使包括间隔件在内的某些燃气涡轮发动机部件变形，膨胀，收缩或平移的力。 这些力可能不利地影响燃气轮机的性能和可靠性，特别是当它们不可预测或难以控制时。 用纤维增强间隔物可能会降低系统重量，更紧凑或可配置的内部包装或高度的增强。
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公开(公告)号：US09169737B2
公开(公告)日：2015-10-27
申请号：US13671205
申请日：2012-11-07
Applicant: United Technologies Corporation
Inventor： Nicholas Aiello , Carney R. Anderson
IPC: F01D11/00
CPC classification number: F01D11/001
Abstract: A rotary seal for sealing a bladed rotor of a gas turbine engine to a stator thereof comprises a sealing element and a sealing element support comprising a radially outer edge portion on which the sealing element is fixed, a radially inner mounting portion adapted to be attached to a supported rotor hub, and a flexible, medial web portion extending between the radially outer edge portion and the radially inner mounting portion.
Abstract translation: 用于将燃气涡轮发动机的叶片转子密封到其定子的旋转密封件包括密封元件和密封元件支撑件，所述密封元件和密封元件支撑件包括固定密封元件的径向外边缘部分，适于附接到 支撑的转子轮毂和在径向外边缘部分和径向内部安装部分之间延伸的柔性内侧腹板部分。
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